design analysis for a small scale engine
DESCRIPTION
DESIGN ANALYSIS for a SMALL SCALE ENGINE. by Tim van Wageningen. Contents - Motivation - Concepts Performance Analysis Conclusions Questions. ±40 min. 2 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS . Nature Technology. small. large. scale →. Atalanta - PowerPoint PPT PresentationTRANSCRIPT
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DESIGN ANALYSISfor a
SMALL SCALE ENGINE
by Tim van Wageningen
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Contents- Motivation- Concepts- Performance Analysis- Conclusions- Questions
±40 min2 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Nature
Technology
scale →
small large
Atalantaproject
3 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Micro Air VehicleFlapping Wing Mechanism
- Designed by Casper Bolsman- 0.6 gram- Performance estimate:
- 0.5 W power output- Needed power density of
system: 125 W/kg- 6 minutes of flight time with
5% efficiency
MAV
4 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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MAV in Action
5 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Hydrogen Peroxide- Master thesis of Arjan Meskers at the PME department, TU Delft
- Chemical energy: high energy density
- Monopropellant
- Clean products: oxygen and water vapor
- Example catalysts: -Manganese oxide
-Silver-Platinum
6 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Catalytic Reaction in Action
7 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Thesis Assignment
Find an engine concept that:- is suitable for the MAV
- 125 W/kg- 5% efficiency
- uses hydrogen peroxide as fuel
8 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Possibilities
9 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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3 different approachesTurbine Piston Cylinder
+
+
+ +
+
10 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept I: Tesla Turbine Engine
+ Easy implementation
+ Theory of Tesla Turbine predicts good efficiency at small scale
- Conversion from rotation to linear motion
+
+
11 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept I: Tesla Turbine Engine
+
+
12 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II: Otto Engine
+ Proven concept on regular scale
- Projects in literature show bad performance because of fluid leakage problem
- Implementation difficult
+
13 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II: Otto engine
+
14 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept III: Hot Air Engine
+ Easy implementation
+ Promising scaling aspects because heat transfer is more effective
- Poor performance on regular scale
+
+
15 MOTIVATIONS - CONCEPTS – PERFORMANCE I / II / III - CONCLUSIONS
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Concept III: Hot Air Engine
+
+
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Performance
- What influences the performance of these concepts?
- Concept I- Concept II- Concept III
- Are the concepts suited for the MAV?- Power density- Efficiency
17 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept I: Tesla Turbine Engine
18 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept I: Tesla Turbine Engine:model
Assumptions:Laminar flow
No entrance effectsIncompressible fluid
19 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Power Efficiency
Pressure difference
Length of belts(radius of discs)
Height of gap(spacing between discs)
20 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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[2] V.G. Krishnan et al. A micro Tesla turbine for power generation from low pressure heads and evaporation driven flows. Transducers, 11:1851 – 1854, June 2011.
Measurements with small scale Tesla turbines
Pressure difference:~20 kPa
Measured Performance45 mW
18% efficiency
Estimated power density:2 W/kg
21 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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- Power density is too low: pressure difference must be increased considerably
- Simple model + measurements show that TTE is not suitable for the current size MAV
Concept I, Tesla Turbine Engine:conclusions
22 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II: Otto Engine
23 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II, Otto Engine: combining 3 models
Catalytic Reaction
Heat Loss
Exhaust Flow + +
24 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Catalytic Reaction: model
25 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
Drop on a catalytic surface
Similar conditions as during experiments
Energy Balance:
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Catalytic Reaction: model
[1] A.J.H. Meskers. High energy density micro-actuation based on gas generation by means of catalyst of liquid chemical energy. Masters thesis, TU Delft, 2010.
26 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Catalytic Reaction: high fuel concentrations
27 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Exhaust Flow: model
Compressible flow through a
round nozzle
Based on momentum
equation
28 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Heat transfer
Heat is transferred via
-conduction-convection-radiation
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Concept II, Otto Engine: combining models
+ + =
- Dealing with model uncertainties:
30 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Otto Engine: observations
-Reaction times are fast enough-Trade off for fuel used per cycle
-Condensation in cylinder31 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II, Otto Engine: Results
- Model shows performance above the current requirements of the MAV (125 W/kg @ 5% efficiency)
32 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept II, Otto Engine: considerations
- Model neglects:- fluid leakage through cylinder/piston gap
- fluid friction at exhaust- fuel delivery system
- Condensation in cylinder problem needs to be addressed
33 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept III: Hot Air Engine
34 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept III, Hot Air Engine:models
+ +
Catalytic Reaction
Heat Loss
Heat Reservoir
s
35 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept III, Hot Air Engine:Catalytic Reaction
Constant temperatureMass balance
36 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Concept III, Hot Air Engine:Heat Reservoirs
Schematic
Under reversibleconditions
Estimate for heat transfer rates
- Using definition Fouriers law
-Optimistic and pessimistic value
37 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Model Results
Resulting performance of model
+ + =
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Considerations for Small Scale Hot Air Engine
- Model neglects losses of - fluid flow between piston cylinder gap
- heat leakage of Decomposition Unit to the working fluid
39 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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Conclusions for Small Scale Hot Air Engine
- Heat transfer is not yet fast enough on this scale, which results in low performance
40 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
- Concept III is not suited for the MAV
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Overall Conclusions
- Of the considered possibilities, the small scale Otto engine is the best option for the MAV:
Power density at 5% efficiency:Concept 1: << 2 W/kg
Concept 2: 245 – 440 W/kgConcept 3: 0.5 – 8 W/kg
41 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
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42 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS
Overall Conclusions
Actual implementation
of concept II requires more detailed
analysis:
- Solving the fluid leakage problem
- Fuel pump- Exhaust port
- Condensation
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43 MOTIVATIONS - CONCEPTS - PERFORMANCE I / II / III - CONCLUSIONS - END
Thank You!
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44 DETAILED SLIDES
Detailed slides
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16 PERFORMANCE
Scaling?
Engine 1S = 1L = 10A = 10V = 10
Engine 2S = 0.5L = 5A = 2.5V = 1.25
Scaling factor
LengthArea
Volume
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6 PREMILAIRY RESEARCH
Approach of others?
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7 PREMILAIRY REASEARCH
Possibilities
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40 PERFORMANCE
Power Efficiency
Pressure difference
Length of belts(radius of disks)
Height of gap(spacing between disks)
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7 CONCEPTS
Energy flow in concepts
Carnot cycle =
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8 PERFORMANCE
Carnot Cycle
zero power output!
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9 PERFORMANCE
Curzon Ahlborn Cycle
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10 PERFORMANCE
Curzon Ahlborn Cycle
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11 PERFORMANCE
ND Curzon Ahlborn Cycle
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17 PERFORMANCE
Basic thermodynamic engine model
- Two constant temperature reservoirs:
- Energy flows modeled with Fouriers law of heat conduction:
-Carnot cycle between the working fluid temperatures:
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ND Curzon Ahlborn Cycle
18 PERFORMANCE
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19 PERFORMANCE
Scaling of performance
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20 PERFORMANCE
Intermediate Conclusions- Efficiency of engine is independent of scale, if the cycle time is adjusted correctly
- Optimal power output can be found by finding the optimal cycle time
- Assuming an optimal engine configuration:
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12 PERFORMANCE
Energy Balance Model
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Energy Balance Model
13 PERFORMANCE
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14 PERFORMANCE
Energy Balance Model
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13 PERFORMANCE
Scaling of optimal cycle time concept 3
opti
pessi
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16 DETAILS
Heat transfer- Heat is transferred via
-conduction-convection-radiation
- FEM model in COMSOL
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Heat transfer: FEM model results
16 DETAILS
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16 DETAILS
Heat transfer: facts for MAV engine
- Low Biot number situations: not much use for insulation.
- Difficult to maintain a temperature difference within the system
- Loss term scaling exponent = 1.5
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Intermediate Conclusions
15 PERFORMANCE
- The performance of depends on a potential and the utilization
- Utilization is independent of scale
- How does this apply to the concepts?
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16 DETAILS
Catalytic Reaction: fundamentals- Decomposition rate proportional to the
effective contact area between fuel and catalyst
- Large Damköhler number: rate temperature independent
- First order reaction:
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32 DETAILS
Exhaust Flow: modelFlow through
a nozzle
Based on momentum
equation
Neglects friction
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Exhaust Flow: characteristics
33 DETAILS
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Model Results: scaling
24 PERFORMANCE
Assuming unrestricted cycle time!
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41 PERFORMANCE
What about scaling?Catalytic Reaction: Fluid Flow:
Power Density at reference scale (S=1):
Power: Power Density:
Power Density when size is 10 times smaller (S=0.1):